The University of Kentucky has been working with ILC Dover, manufacturers of space suits and inflatable space structures, to develop 
inflatable wings that can be used on future space exploration aircraft. Extensive experimentation has been done at UK regarding the aerodynamic performance of the inflatable wings made by ILC Dover. Through the use of computational fluid dynamics thorough testing of different profiles with different bumpy configurations can be analyzed. This can lead to the optimization of an ideal wing for a specific application without the wasteful process of building and analyzing, experimentally, non-ideal wing geometries.
ILC Dover has also provided NACA 4318 based tapered wings that include a two piece construction; the interior is a polyurethane bladder while the exterior is composed of excess Vectran from the construction of the crash bags used on the Mars Rover. The polyurethane/Vectran composition of the wings make them relatively heavy for their size and also require an operating inflation pressure of 15-18psi (gauge). High pressure inflation makes these wings extremely rigid but also making deformation and warping difficult. Each pair of the Vectran wings, also known as FASM wings, are handmade making mass production difficult. Each pair of the FASM wings also has a unique bolt pattern at the root chord requiring experimentalists to fabricate unique test fixtures for each set of wings. 
The FASM wings were used in BIG BLUE IV where they flew a lifting body test bed at ~39lbs with a 4.5hp 50cc engine. A picture of the AIRCAT testbed flying with the inflatable wings is seen here. The most recent wings that ILC Dover have provided to UK for analysis are called MIAV wings. These wings are made of rip-stop nylon and possess the capability of being mass produced. These wings also use the NACA 4318 profile. These wings are not only easily produced, but are relatively light and operate at an inflation pressure of 6-8psi (gauge). The lower pressure makes these wings more applicable to wing deformation/warping methods for roll control. .
The wings that they have provided for analysis include straight Eppler 398 based profile inflatable wings that possess the ability to become rigid when exposed to UV rays. These wings are packaged with a light-curing resin that hardens upon exposure to UV rays in the upper atmosphere. The success of the BIG BLUE Project in May of 2004 demonstrated these capabilities.
Characterization of the flow due to the "bumps" is still not understood entirely. Using the structured, two-dimensional CFD code GHOST, several simulations were computed for the bumpy and smooth Eppler 398 airfoil demonstrative of the inflatable/rigidizable wings used in BIG BLUE I & II. These simulations included laminar simulations, transitional simulations using the Suzen-Huang intermittency transport transition model, and turbulent simulations using Menter's SST turbulence model at Re=25,000 and Re=200,000. Results from the S.-H. transition model predicted relatively large regions where the flow was in transition between fully laminar and fully turbulent characterized by the intermittency variable gamma (see Figures below for gamma contours). The figure on the left is for an angle of attack of 7 degrees. In this figure we see that the S.-H. transition model predicts that the flow is turbulent in the separation region and in transition to approximately 50%c. The figure on the right is for an angle of attack of twenty degrees. In this figure the transition model predicts that the separated shear layer is in transition and that the large stagnant region of separation is mostly laminar due to the essentially stagnant air above the upper surface beyond ~70%c.
In the vorticity contour movies presented below we see the effects of simulating the flow with the transition model at an angle of attack of seven degrees. In the separation region the activity in the laminar simulation is smeared out by the presence of significant values of gamma. However, the vortex shedding at the trailing edge is still present.
It was found that the addition of the bumps tended to decrease the lift of the airfoil, relative to the smooth E398, for the range of angles of attack studied(-2 to 20 degrees). However, the addition of the bumps did tend to increase the stall angle and reduce the amount of separation over the airfoils at Re=25,000. Further details can be obtained by contacting the UK CFD Group.
Relevant Publications:
Reasor, D. A., Lebeau, R. P., Smith, S., Jacob, J. D., "Flight Testing and Simulation of a Mars Aircraft Design Using Inflatable Wings", AIAA Paper 2007-0243, 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, Jan. 2007.
Reasor D.A., LeBeau R.P. "Numerical Investigation of the Effects of Bumps on
Inflatable Wing Profiles" , Region III Student AIAA Conference (2nd Place Master's Presentation/Paper Division), Notre Dame Universtiy, March 2007.
Reasor D.A., LeBeau R.P. "Numerical Study of Bumpy Airfoil Flow Control for Low Reynolds Numbers", AIAA Paper 2007-4100, 37th AIAA Fluid Dynamics Conference and Exhibit, Miami, FL, June 2007.